Abstract: A flange (1) for a space vessel (2), which flange (1) is arranged so as to reduce a shock or impact wave that occurs upon the release of a coupling (5). The coupling (5) is intended to impart a radially inwardly acting force to hold together two separable space vessel parts (3, 4) via two flanges (1, 6) belonging to respective space vessel parts (3, 4). The first flange (1) comprises at least one weakened point (9) so that it has a substantially broken annular shape, in order to thus reduce its energy-absorbing capacity when it is bent inward by the force (F).

Abstract: A joint (4) on a spacecraft (1) for holding together a first craft part (2) and a second craft part, (3) detachable from the first craft part (2). The joint (4) comprises a first flange (5) fixed on the first craft part (2), and a second flange (6) fixed on the second craft part (3), and a number of clamps (7) having a first (7a) and a second (7c) clamp lip, the said clamps being distributed about the periphery of the flanges (5, 6). The clamps transfer radial forces from a tightening device (8), fitted to the clamps (7), so as to fasten the two flanges (5, 6) together. The first flange (5) is clamped between a first clamp surface (7b) on the first clamp lip (7a), and a separation surface (6b) on the second flange (6). These surfaces (7b, 6b) form an acute angle &dgr;, the apex of which is directed in towards the spacecraft (1).

Abstract: A joint (4) on a spacecraft (1) for holding together a first craft part (2) and a second craft part, (3) detachable from the first craft part (2). The joint (4) comprises a first flange (5) fixed on the first craft part (2), and a second flange (6) fixed on the second craft part (3), and a number of clamps (7) having a first (7a) and a second (7c) clamp lip, the said clamps being distributed about the periphery of the flanges (5, 6). The clamps transfer radial forces from a tightening device (8), fitted to the clamps (7), so as to fasten the two flanges (5, 6) together. The first flange (5) is clamped between a first clamp surface (7b) on the first clamp lip (7a), and a separation surface (6b) on the second flange (6). These surfaces (7b, 6b) form an acute angle &dgr;, the apex of which is directed in towards the spacecraft (1).

Abstract: A device for imparting rotational movement to a satellite during discharge from an adapter of a launcher. The satellite includes a first axis, a second axis, and a third axis passing through a center of gravity. The first axis, the second axis, and the third axis are mutually perpendicular. The device includes at least one line dismountably attached to a first point on the satellite and a first point on the adapter. The at least one line is attached to the satellite and the adapter such that the at least one line imparts a rotational movement to the satellite as the satellite is discharged and separates from the adapter with a discharge velocity in a direction along the first axis. A lock dismountably attaches the at least one line to the satellite.

Abstract: A locking device for a band or the like comprising a housing having one end fastened to a first portion of the band. The housing extends in the direction of the prevailing tensile force and is formed with a guide for guiding a link means. This comprises a fastening element fastened at its first end to the second portion of the band and at its second end journally connected to a second link at a distance from its first end. The second link is, at its first end, journaled around an axis provided in the housing transverse to the longitudinal direction of the housing. The locking device also comprises a third link journaled at the first end of the housing and a dowel element which, l via the third link, is able to prevent the second link from being turned around the axis to a position where it is released from the axis so that the locking device is opened.